Results
2014-02-01: We are superseding Airworthiness Directive (AD) 2011-03- [[Page 7383]] 13 for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, and Model CL-600-2D24 (Regional Jet Series 900) airplanes. AD 2011-03-13 required repetitive inspections of the rudder travel limiter (RTL) return springs and primary actuator, and corrective actions if necessary. This new AD requires replacing certain RTL return springs, including doing related investigative and corrective actions, if necessary; which is terminating action for the repetitive inspections. This new AD also revises the applicability. This AD was prompted by reports of failure of the RTL return spring. We are issuing this AD to prevent failure of the RTL, which would permit an increase of rudder authority beyond normal structural limits and consequently affect the controllability of the airplane.
2014-01-04: We are adopting a new airworthiness directive (AD) for all Bae Systems (Operations) Limited Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes. This AD was prompted by reports of excess solder deposited during overhaul on the frangible plug of a fire extinguisher, which prevented the release of the extinguishant. This AD requires a one-time inspection of certain engine and auxiliary power unit (APU) fire extinguishers to determine if the fire extinguishers are affected by excessive solder and corrective actions if necessary. We are issuing this AD to prevent the failure of a fire extinguisher to discharge, which reduces the ability of the fire protection system to extinguish fires in the engine or APU fire zones, possibly resulting in damage to the airplane and injury to the passengers.
99-19-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires repetitive inspections to detect cracking around certain fastener holes and adjacent areas of the front spar of the horizontal stabilizers; and corrective actions, if necessary. This amendment also requires repetitive x-ray inspections, cold working of certain fastener holes of the front spar of the horizontal stabilizers, and follow-on actions; and installation of new fasteners, which constitutes terminating action for the repetitive inspections required by this AD. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the front spar due to fatigue cracking around certain fastener holes of the front spar of the horizontal stabilizers, which could result in reduced structural integrity of the airplane.
48-05-04: 48-05-04 CESSNA: Applies to 120 and 140 Aircraft. Compliance required by April 1, 1948. "This airplane is to be operated in accordance with the flight limitations of the Operations Manual." This refers to the various Airplane Flight Manuals which are required equipment for landplane, skiplane, and seaplane as listed in Aircraft Specification A-768, item 403 and Note 9, which must be carried in the aircraft at all times. Airplane Flight Manuals may be obtained from Cessna dealers and the Cessna Aircraft Co., Wichita, Kansas. (Cessna Service Letters Nos. 32 and 40 dated February 10 and May 6, 1947, respectively, cover this same subject.)
81-06-05 R1: 81-06-05 R1 BELL: Amendment 39-4063 as amended by Amendment 39-4118. Applies to Model 206L-1 helicopters. Paragraph (a) applies to S/N 45154 through 45448. Paragraph (b) applies to helicopters equipped with the BHT IFR Kit. Compliance is required within the next 50 hours' time in service after the effective date of the AD unless already accomplished. To prevent fires due to fuel/oil lines severed by a disintegrating turbine wheel, accomplish the following: (a) Per the instructions in BHT Alert Service Bulletin No. 206L-80-13, "Modification of Engine Fuel Filter, Associated Fuel Hoses and Freewheeling Oil Hoses," dated February 17, 1980, perform the following modifications: (1) On all affected rotorcraft, relocate the fuel filter from its present position to the specified location on the forward firewall. (2) Replace the aft freewheeling oil hose on all affected rotorcraft except rotorcraft equipped with the BHT IFR Kit. (3) As applicable,replace bleed air tubes to avoid an interference at the new filter location. (b) Per the instructions in BHT Alert Service Bulletin No. 206L-81-19, "Replacement of Freewheeling Aft Oil Vent Hose Assembly, P/N 124F001ABB03 11SS," dated February 24, 1981, replace the aft freewheeling oil hose on all affected rotorcraft equipped with BHT IFR Kit. (c) Any alternate method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Bell Helicopter Textron, Product Support Department, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas, and at the FAA Headquarters, 800 Independence Avenue, SW., Washington, D.C. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at their headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. Amendment 39-4063 became effective March 24, 1981. This amendment 39-4118 becomes effective June 1, 1981.
2022-16-03: The FAA is adopting a new airworthiness directive (AD) for certain Continental Aerospace Technologies, Inc. GTSIO-520, IO-346, IO- 470, IO-520, IO-550, LTSIO-520, O-470, TSIO-520, and TSIOL-550 series model reciprocating engines, Lycoming Engines AEIO-320, AEIO-360, AEIO- 540, AIO-320, AIO-360, GO-480, GSO-480, HIO-360, HIO-540, IGO-480, IGO- 540, IGSO-480, IGSO-540, IO-320, IO-360, IO-540, LIO-360, LTIO-540, O- 235, O-320, O-360, O-540, TIGO-541, TIO-360, TIO-540, TIO-541, TVO-435, VO-435, and VO-540 series model reciprocating engines, and Textron Lycoming/Subsidiary of Textron, Inc. IO-720 series model reciprocating engines. This AD was prompted by a report of a manufacturing quality escape of improperly lubricated roller bearings installed in certain magnetos, which may result in overheating and magneto seizure. This AD requires the replacement of affected magneto or inspection of affected magneto and, if no white grease is detected, replacement of magneto components, as applicable, and reassembly of the magneto. The FAA is issuing this AD to address the unsafe condition on these products.
99-19-01: This amendment adopts a new airworthiness directive (AD) that is applicable to Teledyne Continental Motors (TCM) O-470, IO-470, TSIO-470, IO-520, TSIO-520, LTSIO-520, GTSIO-520, IO-550, TSIO-550, and TSIOL-550 series reciprocating engines. This action supersedes priority letter AD 99-09-17 that currently requires a one-time visual and ultrasonic (UT) inspection of the No. 2 and No. 5 crankshaft cheeks for cracks. All crankshafts found with a cracked cheek must be replaced with a serviceable crankshaft prior to further flight. This action adds to the applicability TCM GTSIO-520 series engines and additional engines, identified by serial numbers (S/Ns), of currently affected engine series; references a revised service bulletin that clarifies snap ring installation; increases to 500 hours time-in-service (TIS) the cutoff for engines that require a more immediate inspection; and corrects the contact telephone number for TCM. This amendment is prompted by inspection results from the current priority letter AD. The actions specified by this AD are intended to prevent crankshaft failure due to crankshaft cheek cracks, which could result in total engine power loss, in-flight engine failure, and possible forced landing.
99-18-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 series airplanes, that requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with modified operational procedures to ensure continuous operation with the high pressure cock (HPC) levers in the lockout position. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent burnout of the engines during flight by ensuring that the HPC levers are in a permanent lockout position.
2014-02-05: We are adopting a new airworthiness directive (AD) for Eurocopter Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, and AS350D1 helicopters. This AD requires measuring the distance between the end of the main rotor collective pitch lever (collective) locking stud (locking stud) and the locking strip and repairing the locking stud if the clearance is insufficient. This [[Page 5252]] AD was prompted by a report that insufficient distance between the locking stud and the locking strip may cause the collective to become inadvertently locked in the low pitch (low) position. The actions of this AD are intended to prevent the collective from becoming inadvertently locked in the low position and subsequent loss of control of the helicopter.
2014-02-02: We are adopting a new airworthiness directive (AD) for Bell Model 206L, L-1, L-3, and L-4 helicopters. This AD requires measuring each main rotor (M/R) blade spar space to determine whether it is oversized and reidentifying the M/R blade and [[Page 5250]] reducing the life limit of the blade if the spar spacer is oversized. This AD was prompted by the manufacture of certain blades with an oversized spar spacer and the determination to reduce the life limits of those blades. The actions of this AD are intended to prevent failure of an M/R blade and subsequent loss of control of the helicopter.
99-18-20: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-50, -80A1/A3, and -80C2A series turbofan engines installed on Airbus A300 and A310 series airplanes, that requires initial and repetitive thrust reverser inspections and checks, and allows extended repetitive inspection intervals if an optional double p-seal configuration is installed. This amendment is prompted by the report of a higher than anticipated center drive unit (CDU) cone brake failure rate which reduces the overall thrust reverser system protection against inadvertent deployment. The actions specified by this AD are intended to prevent inadvertent in-flight thrust reverser deployment, which can result in loss of control of the airplane.
71-07-01: 71-07-01 PRATT & WHITNEY: Amdt. 39-1179 as amended by Amendment 39-1279. Applies to Pratt & Whitney Aircraft JT8D-1, -1A, -7, and -7A turbofan engines using Front Compressor Front Hub Part Nos. 504101 and 515201. Pratt & Whitney Aircraft Alert Service Bulletin No. 2944, Revision No. 5, lists the engine and hub serial numbers affected by this airworthiness directive. The manufacturer's serial numbers described in the applicability statement are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received the referenced Alert Service Bulletin from the manufacturer may obtain copies upon request to Pratt & Whitney, Main Street, East Hartford, Conn. These documents may also be examined at Eastern Region headquarters, JFK International Airport, Jamaica, New York. A historical file on this A.D. which includes the incorporated material in full, is maintained by the FAA at its headquarters in Washington, D.C.and at the Eastern Region headquarters, Jamaica, New York. Compliance required as indicated on all front compressor front hubs that have accumulated 6000 cycles or more in service. 1. To preclude failure of the front compressor front hub as a result of (a) possible surface defects in the blade slots or (b) possible loss of effectiveness of shotpeening in the blade slots accomplish the following on hubs listed in tables I and II of the above service bulletin. a. Visually inspect, within the next 150 cycles in service and every 150 cycles in service thereafter until the hub is removed, the rear face and overhung shelf of the hub rim for cracks emanating out of the base of the acute corner of the dovetail slots, or b. Inspect with an eddy current probe, within the next 150 cycles in service, unless already accomplished and every 400 cycles in service thereafter until the hub is removed, the rear overhung shelf of the hub rim for cracks emanating out of the base of the acute corner of the dovetail slots, or c. Within the next 150 cycles in service, unless already accomplished and every 1500 cycles in service thereafter, remove all first stage compressor blades and inspect the blade slots of the hub with an eddy current probe for cracks emanating out of the base of the acute corner of the dovetail slots. d. If any crack is found during any of the foregoing inspections replace hub before further flight. e. It is permissible to use any of the three inspection procedures at the end of the preceding inspection period. 2. To preclude failure of the front compressor front hub from lack of shotpeening accomplish the following on hubs listed in table III of the above service bulletin. a. Visually inspect, within the next 150 cycles in service, to determine whether the rim area of the hub has been shotpeened. b. If the inspection confirms that the hub has not been shotpeened then the hub is to be inspected in accordance with paragraphs 1 (a) through (e) of this AD. Upon submission of substantiating data through an FAA Maintenance Inspector by an owner or operator, the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region, may adjust the compliance time. (Pratt & Whitney Aircraft Alert Service Bulletin No. 2944 Rev. 5 dated 12 August 1971 pertains to this subject.) Amendment 39-1179 was effective March 30, 1971 and was effective upon all recipients of the telegram dated October 16, 1970 which contained this Airworthiness Directive. This amendment 39-1279 is effective September 7, 1971.
2014-01-02: We are adopting a new airworthiness directive (AD) for certain Eurocopter Deutschland GmbH (Eurocopter) Model EC135P2+ and EC135T2+ helicopters. This AD requires inspecting the mechanical air conditioning system compressor bearing block upper bearing (upper bearing) for corrosion, leaking grease, condensation, or water. This AD was prompted by metallic debris from an upper bearing found in the air inlet areas of both engines in a Model EC135P2+ helicopter. The actions of this AD are intended to prevent metallic debris from damaging the engine, causing loss of engine power, and subsequent loss of helicopter control.
86-11-07: 86-11-07 CESSNA: Amendment 39-5324. Applies to the following Model U2O6G and TU206G airplanes modified with Soloy Turbine Pac installations in accordance with Supplemental Type Certificate (STC) number SA2353NM: CESSNA SERIAL NUMBER SOLOY DATA PLATE NUMBER U20603989 763-013 U20604266 763-001 U20604287 763-003 U20604881 763-014 U20605232 763-005 U20605567 763-002 U20605584 763-015 U20605745 763-008 U20605936 763-006 U20606065 763-007 U20606227 763-004 U20606381 763-011 U20606628 763-010 U20606768 763-012 U20606816 763-009 Compliance: Required as indicated in the body of the AD unless previously accomplished. To preclude loss of the in-flight engine restart capability and to correct a condition that could cause erroneous navigation displays to the pilot, accomplish the following: (a) For the above listed airplanes modified by Soloy STC SA2353NM, within the next 100 hours time-in-service (TIS) after the effective dateof this AD, remove and replace the voltage regulator in accordance with the instructions contained in Soloy Service Bulletin (S/B) 04-763 dated March 29, 1985. (b) For serial numbered airplanes U20604266, U20604287, U20605232, U20605567, U20605745, U20605936, U20606065, and U20606227 modified with Soloy STC SA2353NM, within the next 200 hours TIS after the effective date of this AD, modify the electrical system circuit breaker installation in accordance with the instructions contained in Soloy S/B No. 02-763 dated January 7, 1985. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent method of compliance with this AD may be used if approved by the Manager, Seattle Aircraft Certification Office, Federal Aviation Administration, Northwest Mountain Region, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168. All persons affected by this directive may obtain copies of the document referredto herein upon request to Soloy Conversions, LTD., 450 Pat Kennedy Way, S.W., Olympia, Washington 98502 or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on July 4, 1986.
77-07-08: 77-07-08 FAIRCHILD (HILLER): Amendment 39-2866 as amended by Amendment 39-2992. Applies to Model 1100 and FH-1100 type helicopters certified in all categories. Compliance required as follows: To detect improper surface finish in the bolt holes at each end of the tail rotor tension torsion bars, P/N's 24-55106 which could lead to cracking of the bar plates, accomplish the following within the next 25 hours in service after the effective date of this AD unless already accomplished. Inspect the two tail rotor tension torsion bars, P/N's 24-55106 which have serial numbers prior to 1922 or illegible serial numbers, in accordance with Fairchild FH-1100 Service Bulletin No. SBFH1100-55-2A dated 19 January 1977, Section 2 "Accomplishment Instructions" or equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. If tension torsion bars are found unacceptable in accordance with the service bulletin or those procedures approved bythe Chief, Engineering and Manufacturing Branch, replace the bar with one that has been inspected and found acceptable in accordance with the service bulletin or an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection interval specified in this AD. Amendment 39-2866 became effective April 11, 1977. This Amendment 39-2992 becomes effective August 5, 1977.
99-18-11: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-SHERPA, SD3-60 SHERPA, SD3-30, and SD3-60 series airplanes, that requires replacement of the existing bolts that secure the elevator control torque tube bearing housing retaining plate with hex head bolts. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent reduced movement of the elevator controls and consequent reduced controllability of the airplane, as a result of bolts coming loose on the elevator control torque tube bearing housing retaining plate.
2014-01-01: We are adopting a new airworthiness directive (AD) for all Turbomeca S.A. Arrius 2F turboshaft engines. This AD requires a one- time inspection of the ejector assembly nozzle of an affected lubricating device and, if a discrepancy is found, removal and replacement with a part eligible for installation. This AD was prompted by an in-flight shutdown (IFSD) of an Arriel 1 engine. We are issuing this AD to prevent failure of the ejector assembly nozzle, which could lead to an IFSD of the engine, damage to the engine, and damage to the helicopter.
92-27-16: 92-27-16 SABRELINER: Amendment 39-8451. Docket No. 92-NM-229-AD. Applicability: Model NA265, NA265-20, -30, -40, -50, -60, -65, -70, and -80 series airplanes equipped with or converted to electrical driven hydraulic pump (single or double); as listed in Sabreliner Service Bulletin 92-5, dated December 11, 1992; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent electrical arcing, which could lead to fire inside the aft section of the fuselage, accomplish the following: (a) Within 30 days or 10 flight hours after the effective date of this AD, whichever occurs first, install redundant hydraulic pump/motor ground circuitry in accordance with Sabreliner Service Bulletin 92-5, dated December 11, 1992. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Wichita Aircraft Certification Office (ACO),FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The installation shall be done in accordance with Sabreliner Service Bulletin 92-5, dated December 11, 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Sabreliner Corporation, 18118 Chesterfield Airport Road, Chesterfield, Missouri 63005-1121. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue,SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on January 13, 1993.
2013-26-10: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-524G2-19, RB211-524G3-19, RB211-524H-36, and RB211-524H2-19 turbofan engines. This AD requires a one-time reduction in the cyclic life of certain high-pressure (HP) compressor rotor stage 1 and stage 2 discs, and removal of discs that exceed the reduced cycle life. This AD was prompted by a review by RR of the cyclic life of life-limited parts (LLPs) for RB211-524 series engines. We are issuing this AD to prevent the failure of certain LLPs, which could result in uncontained engine damage and damage to the airplane.
99-18-14: This amendment adopts a new airworthiness directive (AD) that applies to Cessna Aircraft Company (Cessna) Model 172R airplanes equipped with a certain modification kit that reduces friction in the elevator control system. This AD requires inspecting the control yoke pivot bolt to assure positive clearance between the pivot bolt s threaded end and aileron direct cable. If positive clearance is not found, this AD requires replacing the control yoke pivot bolt, inspecting the adjacent aileron control cables for damage, and replacing any damaged aileron control cable. This AD is the result of the manufacturer supplying incorrect length control yoke pivot bolts in Cessna Modification Kits MK 172-27-01 that were shipped from September 21, 1998, through April 18, 1999. The actions specified by this AD are intended to prevent failure of an aileron control cable because of an incorrect length control yoke pivot bolt rubbing on one of these cables, which could result in loss of aileron control with loss of directional control of the airplane.
99-18-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that requires installation of strap assemblies on the ceiling panels and rails that support the video monitors. This amendment is prompted by reports of the video monitor ceiling panels falling into the cabin area due to the failure of certain latch assemblies during turbulence. The actions specified by this AD are intended to prevent ceiling panels from falling into the passenger area in the event of failure of certain latch assemblies on the ceiling panels, which could result in consequent injury to the crew and passengers.
93-15-12: 93-15-12 SAAB-SCANIA: Amendment 39-8657. Docket 93-NM-16-AD. Supersedes AD 92-03-08, Amendment 39-8163, which superseded AD 91-07-02, Amendment 39-6932. Applicability: Model SF340A series airplanes, serial numbers 004 through 159, inclusive; and SAAB 340B series airplanes, serial numbers 160 and subsequent; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To ensure proper operation of the main landing gear (MLG) and the nose landing gear (NLG), accomplish the following: (a) Remove the MLG and NLG components identified in the attachments (listed below) to SAAB Service Bulletin SAAB 340-32-066, Revision 1, dated October 17, 1990, and replace them with serviceable components prior to the accumulation of the number of landings listed in the "Fatigue Life Flights" column of the applicable "Life Limited Parts List," or within 60 days after April 15, 1991 (the effective date of AD 91-07-02, Amendment 39-6932), whicheveroccurs later. Thereafter, replace these components with serviceable components at intervals not to exceed the number of landings listed in the "Fatigue Life Flights" column of the applicable "Life Limited Parts List. " SAAB SERVICE BULLETIN SAAB 340-32-066 ATTACHMENTS AP PRECISION HYDRAULICS SERVICE BULLETIN NUMBER DATE ISSUED ATTACHMENT NUMBER AIR83530-32-07 January 1990 1 AIR83570-32-04 January 1990 2 AIR83572-32-01 January 1990 3 AIR84306-32-07 January 1990 4 AIR84350-32-01 January 1990 5 AIR83022-32-18 REV 1 August 1990 6 (b) Remove the MLG and NLG components identified in the attachments (listed below) to SAAB Service Bulletin SAAB 340-32-066, Revision 1, dated October 17, 1990, and replace them with serviceable components prior to the accumulation of the number of landings listed in the "Fatigue Life Flights" column of the applicable "Life Limited Parts List," or within 60 days after March 16, 1992 (the effective date of AD 92-03-08, Amendment 39-8163), whichever occurs later. Thereafter, replace these components with serviceable components at intervals not to exceed the number of landings listed in the "Fatigue Life Flights" column of the applicable "Life Limited Parts List. " SAAB SERVICE BULLETIN SAAB 340-32-066 ATTACHMENTS AP PRECISION HYDRAULICS SERVICE BULLETIN NUMBER DATE ISSUED ATTACHMENT NUMBER AIR83064-32-02 January 1990 7 AIR84310-32-07 January 1990 8 (c) Remove the MLG and NLG components identified in the attachments (listed below) to SAAB Service Bulletin SAAB 340-32-066, Revision 2, dated June 12, 1992, and replace them with serviceable components prior to the accumulation of the number of landings listed in the "Fatigue Life Flights" column of the applicable "Life Limited Parts List," or within 60 days after the effective date of this AD, whichever occurs later. Thereafter, replace these components with serviceable components at intervals not to exceed the number of landings listed in the "Fatigue Life Flights" column of the applicable "Life Limited Parts List. " SAAB SERVICE BULLETIN SAAB 340-32-066 ATTACHMENTS AP PRECISION HYDRAULICS SERVICE BULLETIN NUMBER DATE ISSUED ATTACHMENT NUMBER AIR83530-32-07 REV 1 January 1992 1 AIR83570-32-04 REV 1 January 1992 2 AIR83572-32-01 REV 1 January 1992 3 AIR84306-32-07 REV 1 January 1992 4 AIR84350-32-01 REV 1 January 1992 5 AIR83022-32-18 REV 2 January 1992 6 AIR83064-32-02 REV 1 January 1992 7 AIR84310-32-07 REV 1 January 1992 8 AIR83608-32-01 January 1992 9 (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The modifications shall be done in accordance with SAAB Service Bulletin SAAB 340-32-066, Revision 2, dated June 12, 1992, and SAAB Service Bulletin SAAB 340-32-066, Revision 1, dated October 17, 1990. Revision 2 of SAAB Service Bulletin SAAB 340-32-066 contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page Title Page, 1 2 June 12, 1992 ATTACHMENT 1 1 1 January 1992 2-3 Original January 1990 ATTACHMENT 2 1-2 1 January 1992 ATTACHMENT 3 1 1 January 1992 2 Original June 1990 ATTACHMENT 4 1-2 1 January 1992 ATTACHMENT 51-2 1 January 1992 ATTACHMENT 6 1, 3 2 January 1992 2, 4 Original January 1990 ATTACHMENT 7 1, 3 1 January 1992 2 Original January 1990 ATTACHMENT 8 1 1 January 1992 2-3 Original January 1990 ATTACHMENT 9 1-2 Original January 1992 The incorporation by reference of SAAB Service Bulletin SAAB 340-32-066, Revision 2, dated June 12, 1992, is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. The incorporation by reference of SAAB Service Bulletin SAAB 340-32-066, Revision 1, dated October 17, 1990, was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of March 16, 1992 (57 FR 5376, February 14, 1992). Copies may be obtained from SAAB-SCANIA AB, SAAB Aircraft Product Support, S-581.88, Linkoping, Sweden. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; orat the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on September 17, 1993.
2021-03-15: The FAA is superseding Airworthiness Directive (AD) 2020-13-02 for Leonardo S.p.A. (Leonardo) Model A119 and AW119 MKII helicopters. AD 2020-13-02 required inspecting for movement and the tightening torque of the tail rotor (T/R) plug, the installation of the outboard and inboard faces of the T/R duplex bearing, and the condition of the T/R duplex bearing, T/R plug threads, and nut threads. Depending on the inspection results, AD 2020-13-02 required corrective actions and reporting information. This new AD retains the requirements of AD 2020- 13-02 except the reporting requirement, updates the service information, and requires repeating the inspection. This AD was prompted by Leonardo's update to the service information. The actions of this AD are intended to address an unsafe condition on these products.
99-18-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes. This action requires repetitive inspections and tests of the thrust reverser control and indication system on each engine, and corrective actions, if necessary; installation of a terminating modification; and repetitive operational checks of that installation, and repair, if necessary. This amendment is prompted by the results of a safety review, which revealed that in-flight deployment of a thrust reverser could result in significant reduction in airplane controllability. The actions specified in this AD are intended to ensure the integrity of the fail-safe features of the thrust reverser system by preventing possible failure modes, which could result in inadvertent deployment of a thrust reverser during flight, and consequent reduced controllability of the airplane.
89-02-05: 89-02-05 BF GOODRICH (SARGENT INDUSTRIES, PICO DIVISION): Amendment 39-6106. Applicability: BF Goodrich (or former company name Sargent Industries, PICO Division) 7-man liferaft, P/N 100102-( ). This liferaft is approved under Technical Standard Order C70. NOTE: These liferafts would most likely be used in helicopters or transport category airplanes. Compliance: Required within 90 days after the effective date of this AD, unless previously accomplished. To eliminate cylinders which may leak due to certain material used in their fabrication, accomplish the following: A. Inspect the liferafts to determine the cylinder part number (P/N). If the liferaft contains a P/N 630104-205 cylinder with a serial number listed in BF Goodrich Alert Bulletin No. 130101-25A-203, dated March 29, 1988, the cylinder must be replaced prior to further flight, in accordance with that service bulletin. NOTE: The BF Goodrich service bulletin lists the raft P/N and S/N on which the cylinders were originally installed. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to BF Goodrich Aircraft Evacuation Systems, 3414 South Fifth Street, Phoenix, Arizona 85040. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 3229 East Spring Street, Long Beach, California. This amendment (39-6106, AD 89-02-05) becomes effective February 13, 1989.